EP0694155B1 - A method and an apparatus for imparting to an airborn warhead a desired pattern of movement - Google Patents
A method and an apparatus for imparting to an airborn warhead a desired pattern of movement Download PDFInfo
- Publication number
- EP0694155B1 EP0694155B1 EP94912113A EP94912113A EP0694155B1 EP 0694155 B1 EP0694155 B1 EP 0694155B1 EP 94912113 A EP94912113 A EP 94912113A EP 94912113 A EP94912113 A EP 94912113A EP 0694155 B1 EP0694155 B1 EP 0694155B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- warhead
- canister
- combustion
- disposed
- propellant charge
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
- 238000000034 method Methods 0.000 title claims abstract description 5
- 230000005019 pattern of movement Effects 0.000 title 1
- 238000002485 combustion reaction Methods 0.000 claims abstract description 17
- 239000007789 gas Substances 0.000 claims abstract description 17
- 239000003380 propellant Substances 0.000 claims abstract description 15
- 239000000567 combustion gas Substances 0.000 claims abstract description 7
- 230000033001 locomotion Effects 0.000 claims abstract description 6
- 239000000843 powder Substances 0.000 claims abstract description 5
- 238000007599 discharging Methods 0.000 claims abstract description 4
- 230000001681 protective effect Effects 0.000 claims abstract description 3
- 238000002347 injection Methods 0.000 claims 1
- 239000007924 injection Substances 0.000 claims 1
- IHQKEDIOMGYHEB-UHFFFAOYSA-M sodium dimethylarsinate Chemical class [Na+].C[As](C)([O-])=O IHQKEDIOMGYHEB-UHFFFAOYSA-M 0.000 claims 1
- 239000002775 capsule Substances 0.000 description 21
- 230000000694 effects Effects 0.000 description 13
- 230000006870 function Effects 0.000 description 13
- 238000000926 separation method Methods 0.000 description 4
- 230000001133 acceleration Effects 0.000 description 2
- 230000000979 retarding effect Effects 0.000 description 2
- 230000006641 stabilisation Effects 0.000 description 2
- 238000011105 stabilization Methods 0.000 description 2
- 241001415801 Sulidae Species 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000036461 convulsion Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000008571 general function Effects 0.000 description 1
- 238000005065 mining Methods 0.000 description 1
- 230000009993 protective function Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
- F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
- F42B10/58—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding of rotochute type
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
- F42B10/26—Stabilising arrangements using spin
- F42B10/28—Stabilising arrangements using spin induced by gas action
- F42B10/30—Stabilising arrangements using spin induced by gas action using rocket motor nozzles
Definitions
- the present invention relates to a method and an apparatus for transferring such warheads as, provided with their own target seekers, are discharged into ballistic trajectories in non-rotary state, from this first non-rotary state in which warhead and target seeker are inactivated, to a second fully developed rotary state during the downward section of the trajectory in which the warhead is spun up about its major axis of inertia to a predetermined speed, given a fall velocity which is predetermined during this search and effect phase determined by specific aerodynamic brake surfaces activated in connection therewith, and a stable fall trajectory with the centre of the warhead and main axes of inertia directed in a predetermined manner in relation to the fall trajectory at the same time as the target seeker is activated for seeking a subjacent target area, and the effective charge of the warhead is made ready, in the event of identification of a target by the target seeker, to be discharged in the search direction thereof for combatting the target.
- That warhead which is referred to here is, thus, to be given a complex trajectory in which the problem resides in imparting, within the shortest possible launch trajectory, to the warhead a sufficiently long fall trajectory for its seek and effect phase at the same time as the non-rotary state of the warhead, before its active seek and effect phase has been commenced, must have been transferred to a rotary state and given a stable fall trajectory for which a plurality of specific requirements must be established in respect of the direction and rotation of the warhead.
- warheads of similar type it is previously known to releasibly house them in a protected canister up to that point in time when their target seeker and aerodynamic brake surfaces are to be activated and then, with the aid of a pyrotechnic charge, eject the warhead out of the canister, whereupon target seeker and brake surfaces are flipped out by spring force and/or under the action of the inertia forces and aerodynamic forces acting on the warhead.
- a warhead of this particular type is described in EP-A-0 252 036 (preamble of claim 1).
- the problem which has been solved by means of the present invention, see claim 1, is, in a continuous and unbroken sequence, to impart to the warhead its above-mentioned rotation and, in connection therewith, to eject it out from its protective canister.
- the warhead contemplated here functions in basically the same manner as corresponding warheads of previously known type which are allocated to a relevant target area by a rotation-stabilized projectile such as an artillery shell or the like and from which the complete warhead is separated when the projectile reaches the immediate proximity of the target area in order thereafter to be retarded to the desired values both in respect of rotation and fall velocity, and is given the same type of stable fall trajectory and general direction as the warhead according to the present invention.
- a rotation-stabilized projectile such as an artillery shell or the like
- That vehicle which is referred to in this context may, for example, consist of a cruise missile with its own target seeker which carries a large number of complete warheads which it may eject when its own target seeker has identified the target, or alternatively the capsule may consist of a part in a permanent booby trap mining or the like.
- the warheads of the type under consideration here will, as soon as they have reached the seek and effect phase, function in exactly the same manner irrespective of whether they were transported to the target area by a rotary vehicle such as an artillery shell or a capsule of other type from which they are initially ejected under non-rotary conditions.
- a rotary vehicle such as an artillery shell or a capsule of other type from which they are initially ejected under non-rotary conditions.
- ejection from a non-rotary vehicle (which moreover generally moves closer to ground level) places other specific requirements on the function stages prior to the search and effect phase. This also implies demands on a number of components which are not necessary in the alternative employing an artillery shell as vehicle.
- warheads of this general type are described in the European patents and European applications listed below: 0 252 036; 0 424 337; 0 451 123; 0 587 970; 0 587 969; 0 540 484; 0 539 340.
- the general function of the warheads under consideration here are, in this instance, described in the first of these patents, while the remaining publications primarily relate to different partial solutions of which not all must, of necessity, be included in the warheads pertinent to the present invention.
- the mechanical stresses on the warheads will be greater if they are transported to the target area by an artillery shell than if they are conveyed to the target area by an aerodynamic capsule and only ejected from the capsule when in the immediate proximity of the target area.
- the warhead which, as was intimated by way of introduction, is included in a capsule which follows an aerodynamic, non-rotary trajectory relatively close to ground level, or is fixedly placed therein, the warhead must, hence, first be given sufficient flight altitude in the form of a ballistic launch trajectory by, for example, a pyrotechnically activated launching from the capsule at a point in time and in a direction predetermined beforehand in relation to the contemplated target area, and, in connection with or in immediate association with the ejection is, in addition to the initially necessary flight altitude also given the desired rotation and a stable fall trajectory of a predetermined fall velocity during which target seeker and warhead must be activated.
- the warhead must be rotated about a major axis of inertia which makes a predetermined angle with the main axes of the target seeker and the warhead, in order to realize the helical scanning or target seeking of the target area as described in EP 0 252 036.
- the capsule From a long distance the capsule is launched in a direction towards that region where the target is assumed to be.
- the relevant number of complete warheads is ejected out of the capsule. This is put into effect preferably rearwardly at an angle determined in view of the flight speed of the capsule.
- the warhead may be put into a desired ballistic trajectory which takes it to a predetermined point above the identified target. If the ejection out of the capsule is effected using a rocket launcher, this should, as soon as it is no longer needed, be discarded from the second main stage of the warhead, hereinafter referred to as the cylinder.
- the cylinder, of the warhead has reached the zenith of its new ballistic trajectory, it may be necessary to retard its pendulum movements. This may be effected by means of a parachute which, after the cylinder has passed its own trajectory zenith, will assume the more regular function of a parachute.
- the cylinder Once the cylinder has passed the zenith of the ballistic trajectory and been retarded to a substantially vertical fall trajectory, it is important to impart to the actual warhead a carefully predetermined rotation and to activate its target seeker and those brake surfaces which are to control its continued fall trajectory. All of this must be carried out so that the warhead will have a stable fall trajectory rotating about' a major axis of inertia which, as closely as possible, coincides with the trajectory tangent while the effected direction of the warhead and the scanning direction of the target seeker make an angle with the trajectory tangent.
- the present invention primarily relates to this final stage in which the warhead is given the desired rotation and its target seeker and ultimate brake surfaces are activated.
- the target seeker and the brake surfaces are activated by being flipped out, at the same time as the warhead is given the desired rotation and is released from the previously mentioned canister with its parachute.
- These flip-out brake surfaces may be of the type described in EP 901 503 25.3 and their design is of major importance so as to impart to the warhead a pendulum-free fall trajectory towards ground level.
- the target seeker may also be of the type which is intimated in EP-A-0 424 337.
- the warhead relevant in the present context is, thus, initially (i.e. from the starting position in the capsule) enclosed in a canister which is separably joined with a rocket motor for ejecting it from the capsule.
- the canister is in the form of a cylinder open at one end and in which the actual warhead is ejectably housed.
- the devices characteristic of the present invention are housed in the closed end of the canister.
- a canister which merely has a protective function and without any of the devices particularly distinctive of the present invention is described in EP 928 502 38.4.
- the rocket motor activated on command from the target seeker of the capsule thus ejects out the cylinder, i.e. the canister plus warhead, which, after separation from the rocket motor will enter into the previously intimated ballistic launch trajectory.
- the parachute necessary for such factors as retarding any possible pendulum movements will be opened out as intimated previously.
- the parachute When the cylinder has reached the zenith of the ballistic trajectory, the parachute is transformed from previously having been more of a pendulum brake to serving a more purely defined parachute function.
- a combined function designed in accordance with the present invention is activated for imparting to the warhead the rotation necessary for the continued trajectory and ejection of the warhead out of the canister.
- the canister has been equipped with an annular combustion chamber which is disposed concentrically about the main axis of the canister and is provided with one or more gas outlet nozzles whose outlet direction makes, an angle with the radius of the combustion chamber passing therethrough, i.e. they are more or less tangential.
- a similarly annular propellant charge which, with its one broad side, covers one or more gas outlets discharging in a direction towards the warhead while its other broad side is free to be ignited by a pyrocharge disposed in the centre of the canister and initiated by the time function.
- a displaceable sabot which, when it is actuated on by the gas pressure from the combustion chamber, forces out the warhead out of the canister.
- the operational cycle will thus be that the cylinder first spins up in speed by means of the combustion gases flowing out through the more or less tangentially disposed gas outlet nozzles, while the warhead is only then acted on when the gas outlets directed towards the warhead have been opened in that the propellant is more or less burned out, via the displaceable sabot and is forced out of the canister, whereupon the target seeker and the warhead's own aerodynamic brake surfaces (which have been held in the collapsed position by the canister wall, are flipped out and the target seeker is activated).
- the complete warhead 1 illustrated in Fig. 1 includes the so-called cylinder, consisting of a canister 2 and a warhead 3 mounted therein against its effective charge 7 and various accessories such as target seeker etc. and a rocket motor 4.
- the cylinder and rocket motor are held together by a releasable joint 5 in the form of a simple lap joint between them.
- a releasable joint 5 in the form of a simple lap joint between them.
- the rocket motor 4 is a powder rocket motor with, for example, seven outlet nozzles 6, three of which are visible on the figure, this to impart a sufficiently rapid impulse.
- the barrel or tube in which the rocket motor - cylinder of the combination is to be mounted must, namely, be made very short for reasons of necessity.
- the cylinder thus includes the canister 2 and the warhead 3.
- the effective charge 7 included in the warhead may, for example, be a projectile-forming directed effect charge.
- the target seeker is designated with reference No. 8. These details have, like the brake surfaces 9 and 10, not been drawn on Fig. 1, since there they are completely collapsed in place. The appearance of the details 8-10 is most clearly apparent from Figs. 5 and 6 where they are shown in the flipped-out position.
- a parachute 12 is packed.
- This latter is secured in the canister as a fitting 13.
- an annual combustion chamber 15 In the end of the canister facing towards the rocket motor there is further disposed an annual combustion chamber 15 whose appearance is even more clearly apparent from Fig. 2.
- This is associated with a centrally located ignition charge 16 which, via four non-return valves 17-20, is in communication with the combustion chamber 15 in which an annular propellant charge 21 is disposed.
- the propellant charge is glued against the end wall 22 of the combustion chamber 15 turned to face the warhead 3, and it thereby covers a number (in the present case 4) of gas outlets 23-26 directed towards the warhead 3.
- the other broad side of the propellant charge 21 is open for ignition.
- the combustion chamber 15 is further provided with four substantially tangential gas outlet nozzles 27-30 (see also Fig. 29).
- the gas outlets 23-26 discharge in an annular chamber 31 behind a displaceable sabot 32 which, when it is shifted, will jerk the warhead 3 out of the canister 2.
- a displaceable sabot 32 which, when it is shifted, will jerk the warhead 3 out of the canister 2.
- two support halves 34 and 35 are disposed (cf. Fig. 5).
- the substantially complete warhead 1 described together with Fig. 1 is, as is apparent from Fig. 3, intended to be mounted, together with a number of identical warheads, each in their barrel or tube 36 in a capsule 37.
- the ejection is affected in an angle a rearwardly in the direction of travel of the capsule 37. This will impart to the warhead a ballistic ejection trajectory in the direction of the sketched trajectory tangent.
- the ejection preferably takes place on command from a target seeker integrated in the capsule when this has identified combat-worthy targets M. (See Fig. 4.)
- the different functional stages up to and including the point when the target seeker of the warhead has been activated and the seek and effect phase commenced may, for example, be controlled by a time function integrated in the target seeker 8 of the warhead which is activated when the cylinder is ejected out of the capsule (cruise missile).
- a downward stabilization is commenced in the trajectory in order, thereafter, at point 40, to merge into a rotation and separation phase.
- the cylinder is then dependent in the parachute 12 and its axis may not move more than a predetermined number of degrees from the vertical.
- the rotation and separation phase is introduced by the pyrocharge 33 being initiated by the previously intimated time function and, in its turn, ignites the pyrocharge 16 which in turn ignites the propellant charge 21 via the non-return valve 17-20, whereafter the non-return valves are closed and the combustion gases begin to flow out through the nozzle 27-30 and (because these are substantially tangentially directed) thereupon begins to accelerate the cylinder in rotational speed.
- the propellant charge 21 When the propellant charge 21 has essentially burned out, it brakes over the gas outlets 23-26 and the combustion gases begin to flow into the chamber 31, whereupon the sabot 32 forces the warhead 3 out of the canister 2 once the gas pressure has first entailed that safety devices in the form of pins or the like have first been eliminated.
- the warhead rotates in the initial phase about the line of symmetry of the included effective charge, which, however, because the target seeker 8 has been flipped out beside it, does not coincide with the main axis of inertia of the warhead.
- the target seeker and the line of symmetry of the effective charge will, by the rotation and simultaneous fall motion in the trajectory tangent, follow a helically continuous curve in towards the centre which cover and is prepared to combat targets within a predetermined target area on ground level.
- a certain time is required, i.e. the fall distance for the warhead 3 in accordance with the previously described example, to assume its stable position of rotation about the main axis of inertia, since it is initially rotated about the axis of symmetry of the effective charge.
- this time may be shortened and probably completely eliminated if the warhead is, already at the initial stage, spun up about that axis which defines the position of the main axis of inertia when the target seeker and brake surfaces are flipped out.
- This may either be effected in that the nozzles 27-30 are given asymmetric placement, or alternatively in that the warhead is placed obliquely in the canister.
- a canister 41 of oval cross-section is employed.
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Radar Systems Or Details Thereof (AREA)
- Air Bags (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Laminated Bodies (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
- Manufacture, Treatment Of Glass Fibers (AREA)
- Woven Fabrics (AREA)
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
SE9301038 | 1993-03-30 | ||
SE9301038A SE501082C2 (sv) | 1993-03-30 | 1993-03-30 | Sätt och anordning för att ge en luftburen stridsdel ett önskat rörelsemönster |
PCT/SE1994/000232 WO1994023265A1 (en) | 1993-03-30 | 1994-03-17 | A method and an apparatus for imparting to an airborn warhead a desired pattern of movement |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0694155A1 EP0694155A1 (en) | 1996-01-31 |
EP0694155B1 true EP0694155B1 (en) | 2000-01-12 |
Family
ID=20389397
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP94912113A Expired - Lifetime EP0694155B1 (en) | 1993-03-30 | 1994-03-17 | A method and an apparatus for imparting to an airborn warhead a desired pattern of movement |
Country Status (9)
Country | Link |
---|---|
US (1) | US5679919A (ja) |
EP (1) | EP0694155B1 (ja) |
JP (1) | JP3466615B2 (ja) |
CA (1) | CA2159345C (ja) |
DE (1) | DE69422617T2 (ja) |
IL (1) | IL109071A (ja) |
NO (1) | NO309693B1 (ja) |
SE (1) | SE501082C2 (ja) |
WO (1) | WO1994023265A1 (ja) |
Families Citing this family (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
SE505189C2 (sv) * | 1994-11-16 | 1997-07-14 | Bofors Ab | Sätt och anordning för att med från en bärfarkost frigjorda stridsdelar bekämpa längs bärfarkostens färdväg identifierade mål |
US5631830A (en) | 1995-02-03 | 1997-05-20 | Loral Vought Systems Corporation | Dual-control scheme for improved missle maneuverability |
US6308911B1 (en) | 1998-10-30 | 2001-10-30 | Lockheed Martin Corp. | Method and apparatus for rapidly turning a vehicle in a fluid medium |
US6478250B1 (en) * | 1999-10-12 | 2002-11-12 | Raytheon Company | Propulsive torque motor |
US6666145B1 (en) * | 2001-11-16 | 2003-12-23 | Textron Systems Corporation | Self extracting submunition |
US20090223403A1 (en) * | 2006-01-10 | 2009-09-10 | Harding David K | Warhead delivery system |
US8468923B2 (en) * | 2007-02-16 | 2013-06-25 | Lockheed Martin Corporation | Apparatus and method for selectively affecting a launch trajectory of a projectile |
US9587922B2 (en) * | 2013-04-12 | 2017-03-07 | Raytheon Company | Attack capability enhancing ballistic sabot |
Family Cites Families (26)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
NL135093C (ja) * | 1966-03-22 | |||
US3457861A (en) * | 1968-01-25 | 1969-07-29 | Us Navy | Missile booster pressure control mechanism |
US3724782A (en) * | 1971-07-22 | 1973-04-03 | Us Navy | Deployable aerodynamic ring stabilizer |
US3771445A (en) * | 1972-01-17 | 1973-11-13 | Universal Labor Inc | Method for decoratively silk screen printing candles |
JPS4888800A (ja) * | 1972-02-26 | 1973-11-20 | ||
US3771455A (en) * | 1972-06-06 | 1973-11-13 | Us Army | Flechette weapon system |
SE432670B (sv) * | 1979-09-27 | 1984-04-09 | Kurt Andersson | Sett att stabilisera en artilleriprojektil och i slutfasen korrigera dess bana och artilleriprojektil for genomforande av settet |
US4625646A (en) * | 1980-10-06 | 1986-12-02 | The Boeing Aerospace Company | Aerial missile having multiple submissiles with individual control of submissible ejection |
FR2536720A1 (fr) * | 1982-11-29 | 1984-06-01 | Aerospatiale | Systeme pour le pilotage d'un missile au moyen de jets gazeux lateraux et missile comportant un tel systeme |
DE3525147C1 (de) * | 1985-07-13 | 1987-01-15 | Diehl Gmbh & Co | Sturz-Flugkoerper zum Bekaempfen von insbesondere Radarstellungen |
DE3686321T2 (de) * | 1985-10-31 | 1992-12-17 | British Aerospace | Ausstossantrieb fuer flugkoerper. |
SE452505B (sv) * | 1986-03-27 | 1987-11-30 | Bofors Ab | Substridsdel med svengbart anordnad maldetektor |
FR2686687B1 (fr) * | 1987-04-22 | 1994-05-13 | Thomson Brandt Armements | Procede et dispositif de pilotage d'un projectile selon ses trois axes de roulis tangage et lacet. |
US5158246A (en) * | 1988-11-15 | 1992-10-27 | Anderson Jr Carl W | Radial bleed total thrust control apparatus and method for a rocket propelled missile |
FR2643981B1 (fr) * | 1989-03-03 | 1994-03-11 | Thomson Brandt Armements | Systeme de guidage d'un vecteur par jets de gaz continus |
SE464834B (sv) * | 1989-10-20 | 1991-06-17 | Bofors Ab | Substridsdel med svaengbara baerytor |
SE465440B (sv) * | 1990-04-04 | 1991-09-09 | Bofors Ab | Substridsdel |
SE468261B (sv) * | 1991-04-08 | 1992-11-30 | Bofors Ab | Substridsdel anordnad att avskiljas fraan en flygkropp |
SE468262B (sv) * | 1991-04-08 | 1992-11-30 | Bofors Ab | Substridsdel anordnad att avskiljas fraan en flygkropp |
DE4123649C2 (de) * | 1991-07-17 | 1993-11-11 | Rheinmetall Gmbh | Ausstoßvorrichtung |
SE9102702L (sv) * | 1991-09-18 | 1993-03-19 | Bofors Ab | Stridsdel |
SE468568B (sv) * | 1991-10-23 | 1993-02-08 | Bofors Ab | Saett att fraan en skyddskanister separera substridsdelar samt skyddskanister |
FR2683310B1 (fr) * | 1991-11-06 | 1993-12-31 | Giat Industries | Dispositif d'ejection d'elements de charge utile hors de l'enveloppe d'un obus cargo. |
SE503719C2 (sv) * | 1992-06-30 | 1996-08-12 | Bofors Ab | Sätt och anordning för separation av substridsdelar |
FR2695992B1 (fr) * | 1992-09-21 | 1994-12-30 | Giat Ind Sa | Sous munition à effet dirigé. |
SE508475C2 (sv) * | 1993-03-30 | 1998-10-12 | Bofors Ab | Sätt och anordning för spridning av stridsdelar |
-
1993
- 1993-03-30 SE SE9301038A patent/SE501082C2/sv not_active IP Right Cessation
-
1994
- 1994-03-17 CA CA002159345A patent/CA2159345C/en not_active Expired - Fee Related
- 1994-03-17 WO PCT/SE1994/000232 patent/WO1994023265A1/en active IP Right Grant
- 1994-03-17 DE DE69422617T patent/DE69422617T2/de not_active Expired - Fee Related
- 1994-03-17 US US08/525,734 patent/US5679919A/en not_active Expired - Fee Related
- 1994-03-17 JP JP52197194A patent/JP3466615B2/ja not_active Expired - Fee Related
- 1994-03-17 EP EP94912113A patent/EP0694155B1/en not_active Expired - Lifetime
- 1994-03-22 IL IL10907194A patent/IL109071A/xx not_active IP Right Cessation
-
1995
- 1995-09-29 NO NO953880A patent/NO309693B1/no unknown
Also Published As
Publication number | Publication date |
---|---|
SE9301038L (sv) | 1994-10-01 |
CA2159345A1 (en) | 1994-10-13 |
NO953880L (no) | 1995-09-29 |
IL109071A (en) | 2000-02-29 |
US5679919A (en) | 1997-10-21 |
SE9301038D0 (sv) | 1993-03-30 |
WO1994023265A1 (en) | 1994-10-13 |
EP0694155A1 (en) | 1996-01-31 |
NO953880D0 (no) | 1995-09-29 |
CA2159345C (en) | 2005-01-18 |
SE501082C2 (sv) | 1994-11-07 |
JPH08508564A (ja) | 1996-09-10 |
JP3466615B2 (ja) | 2003-11-17 |
NO309693B1 (no) | 2001-03-12 |
DE69422617D1 (de) | 2000-02-17 |
DE69422617T2 (de) | 2000-08-10 |
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